63848 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model EMB–550 

airplane must comply with the fuel vent 

and exhaust emission requirements of 

14 CFR part 34 and the noise 

certification requirements of 14 CFR 36 

and the FAA must issue a finding of 

regulatory adequacy under § 611 of 

Public Law 92 574, the ‘‘Noise Control 

Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.17(a)(2). 

Novel or Unusual Design Features 

The Embraer S.A. Model EMB–550 

airplane will incorporate the following 

novel or unusual design features: digital 

systems architecture composed of 

several connected networks. The 

proposed architecture and network 

configuration may be used for, or 

interfaced with, a diverse set of 

functions, including: 

1. Flight-safety related control, 

communication, display, monitoring, 

and navigation systems (aircraft control 

functions); 

2. Airline business and administrative 

support (airline information services); 

3. Passenger information and 

entertainment systems (passenger 

entertainment services); and, 

4. The capability to allow access to or 

by systems external to the airplane. 

Discussion 

The proposed Model EMB–550 

architecture and network configuration 

may allow increased connectivity to and 

access by external airplane sources, 

airline operations, and maintenance 

systems to the aircraft control functions 

and airline information services. The 

aircraft control and airline information 

functions perform actions required for 

the safe operation and maintenance of 

the airplane. Previously, these functions 

had very limited connectivity with 

external sources. 

The architecture and network 

configuration may allow the 

exploitation of network security 

vulnerabilities resulting in intentional 

or unintentional destruction, disruption, 

degradation, or exploitation of data, 

systems, and networks critical to the 

safety and maintenance of the airplane. 

The existing regulations and guidance 

material did not anticipate these types 

of airplane system architectures. 

Furthermore, 14 CFR regulations and 

current system safety assessment policy 

and techniques do not address potential 

security vulnerabilities, which could be 

exploited by unauthorized access to 

airplane systems, data buses, and 

servers. Therefore, these special 

conditions and a means of compliance 

are issued to ensure that the security 

(i.e., confidentiality, integrity, and 

availability) of airplane systems is not 

compromised by unauthorized wired or 

wireless electronic connections. 

Applicability 

As discussed above, these special 

conditions are applicable to the Embraer 

S.A. Model EMB–550 airplane. Should 

Embraer S.A. apply at a later date for a 

change to the type certificate to include 

another model incorporating the same 

novel or unusual design feature, the 

special conditions would apply to that 

model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

prior public comment would result in a 

significant change from the substance 

contained herein. The FAA is requesting 

comments to allow interested persons to 

submit views that may not have been 

submitted in response to the prior 

opportunities for comment described 

above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Embraer S.A. 

Model EMB–550 airplanes. 

Airplane Electronic System Security 

Protection From Unauthorized External 

Access 

1. The applicant must ensure airplane 

electronic system security protection 

from access by unauthorized sources 

external to the airplane, including those 

possibly caused by maintenance 

activity. 

2. The applicant must ensure that 

electronic system security threats are 

identified and assessed, and that 

effective electronic system security 

protection strategies are implemented to 

protect the airplane from all adverse 

impacts on safety, functionality, and 

continued airworthiness. 

3. The applicant must establish 

appropriate procedures to allow the 

operator to ensure that continued 

airworthiness of the airplane is 

maintained, including all post typecertification modifications that may 

have an impact on the approved 

electronic system security safeguards. 

November 29, 2013. 

Issued in Renton, Washington, on 

September 6, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24989 Filed 10–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0776; Special 

Conditions No. 25–498–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplanes; Sidestick 

Controllers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special condition; request 

for comments. 

SUMMARY: These special conditions are 

issued for the Embraer S.A. Model 

EMB–550 airplane. This airplane will 

have a novel or unusual design feature 

associated with sidestick controllers. 

The applicable airworthiness 

regulations do not contain adequate or 

appropriate safety standards for this 

design feature. These special conditions 

contain the additional safety standards 

that the Administrator considers 

necessary to establish a level of safety 

equivalent to that established by the 

existing airworthiness standards. 

DATES: The effective date of these 

special conditions is October 25, 2013. 

We must receive your comments by 

December 9, 2013. 

ADDRESSES: Send comments identified 

by docket number FAA–2013–0776 

using any of the following methods: 

• Federal eRegulations Portal: Go to 

http://www.regulations.gov/ and follow 

the online instructions for sending your 

comments electronically. 

Mail: Send comments to Docket 

Operations, M–30, U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations 63849 

Building Ground Floor, Washington, DC 

20590–0001. 

Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 8 

a.m. and 5 p.m., Monday through 

Friday, except federal holidays. 

Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://www.regulations.gov/, 

including any personal information the 

commenter provides. Using the search 

function of the docket Web site, anyone 

can find and read the electronic form of 

all comments received into any FAA 

docket, including the name of the 

individual sending the comment (or 

signing the comment for an association, 

business, labor union, etc.). DOT’s 

complete Privacy Act Statement can be 

found in the Federal Register published 

on April 11, 2000 (65 FR 19477–19478), 

as well as at http:// 

DocketsInfo.dot.gov/. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov/ at any time. 

Follow the online instructions for 

accessing the docket or go to the Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except federal holidays. 

FOR FURTHER INFORMATION CONTACT: 

Loran Haworth, FAA, Airplane and 

Flight Crew Interface Branch, ANM– 

111, Transport Airplane Directorate, 

Aircraft Certification Service, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; telephone 425–227–1133; 

facsimile 425–227–1149. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 

on, these special conditions are 

unnecessary because the substance of 

these special conditions has been 

subject to the public comment process 

in several prior instances with no 

substantive comments received. The 

FAA therefore finds that good cause 

exists for making these special 

conditions effective upon publication. 

Comments Invited 

We invite interested people to take 

part in this rulemaking by sending 

written comments, data, or views. The 

most helpful comments reference a 

specific portion of the special 

conditions, explain the reason for any 

recommended change, and include 

supporting data. 

We will consider all comments we 

receive by the closing date for 

comments. We may change these special 

conditions based on the comments we 

receive. 

Background 

On May 14, 2009, Embraer S.A. 

applied for a type certificate for their 

new Model EMB–550 airplane. The 

Model EMB–550 airplane is the first of 

a new family of jet airplanes designed 

for corporate flight, fractional, charter, 

and private owner operations. The 

aircraft has a conventional configuration 

with low wing and T-tail empennage. 

The primary structure is metal with 

composite empennage and control 

surfaces. The Model EMB–550 airplane 

is designed for 8 passengers, with a 

maximum of 12 passengers. It is 

equipped with two Honeywell 

HTF7500–E medium bypass ratio 

turbofan engines mounted on aft 

fuselage pylons. Each engine produces 

approximately 6,540 pounds of thrust 

for normal takeoff. The primary flight 

controls consist of hydraulically 

powered fly-by-wire elevators, ailerons 

and rudder, controlled by the pilot or 

copilot sidestick. 

The Model EMB–550 airplane will 

use passive sidestick controllers for 

pitch and roll control instead of a 

conventional control column and wheel. 

The main characteristics of a sidestick 

controller are: 

• Passive inceptor (i.e., the hand grip 

returns to the null position after in/out 

movements), 

• Artificial tactile feedback, 

• Located on the side of the pilot, and 

• No mechanical interconnection. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.17, 

Embraer, S.A. must show that the Model 

EMB–550 airplane meets the applicable 

provisions of part 25, as amended by 

Amendment 25–1 through 25–127 

thereto. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the Model EMB–550 airplane 

because of a novel or unusual design 

feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same novel or unusual 

design feature, the special conditions 

would also apply to the other model. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model EMB–550 

airplane must comply with the fuel vent 

and exhaust emission requirements of 

14 CFR part 34 and the noise 

certification requirements of 14 CFR 

part 36; and the FAA must issue a 

finding of regulatory adequacy under 

§ 611 of Public Law 92–574, the ‘‘Noise 

Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.17(a)(2). 

Novel or Unusual Design Features 

The Model EMB–550 airplane will 

incorporate the following novel or 

unusual design features: The Model 

EMB–550 airplane has a sidestick 

controller for pitch and roll control. 

Discussion 

Regulatory requirements for 

conventional wheel and column 

controllers, such as requirements 

pertaining to pilot strength and 

controllability, are not directly 

applicable to sidestick controllers. 

Certain ergonomic considerations such 

as armrest support, freedom of arm 

movement, controller displacement, 

handgrip size and accommodations for 

a range of pilot sizes are not addressed 

in the regulations. In addition, pilot 

control authority may be uncertain, 

because the sidestick controllers are not 

mechanically interconnected as with 

conventional wheel and column 

controls. Pitch and roll control force and 

displacement sensitivity must be 

compatible so that normal inputs on one 

control axis do not cause significant 

unintentional inputs on the other. As a 

result, a special condition is issued to 

require that the unique features of the 

sidesstick controller must be 

demonstrated through flight and 

simulator tests to have suitable handing 

and control characteristics. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

EMB–550 airplane. Should Embraer 

S.A. apply at a later date for a change 

to the type certificate to include another 

model incorporating the same novel or 

unusual design feature, the special 

conditions would apply to that model as 

well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability. 


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63850 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

prior public comment would result in a 

significant change from the substance 

contained herein. Therefore, the FAA 

has determined that prior public notice 

and comment are unnecessary, and good 

cause exists for adopting these special 

conditions upon issuance. The FAA is 

requesting comments to allow interested 

persons to submit views that may not 

have been submitted in response to the 

prior opportunities for comment 

described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Embraer S.A. 

Model EMB–550 airplanes. 

In the absence of specific 

requirements for sidestick controllers, 

the following Special Conditions apply: 

1. Pilot strength: In lieu of the control 

force limits shown in § 25.143(d) for 

pitch and roll and in lieu of the specific 

pitch force requirements of 

§§ 25.143(i)(2), 25.145(b), and 25.175(d), 

it must be shown that the temporary and 

maximum prolonged force levels for the 

sidestick controllers are suitable for all 

expected operating conditions and 

configurations, whether normal or nonnormal. 

2. Pilot control authority: The 

electronic sidestick controller coupling 

design must provide for corrective and/ 

or overriding control inputs by either 

pilot with no unsafe characteristics. 

Annunciation of the controller status 

must be provided and must not be 

confusing to the flightcrew. 

3. Pilot control: It must be shown by 

flight tests that the use of sidestick 

controllers does not produce unsuitable 

pilot-in-the-loop control characteristics 

when considering precision path 

control/tasks and turbulence. In 

addition, pitch and roll control force 

and displacement sensitivity must be 

compatible, so that normal inputs on 

one control axis will not cause 

significant unintentional inputs on the 

other. 

Issued in Renton, Washington, on 

September 6, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25206 Filed 10–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0881; Directorate 

Identifier 2013–SW–056–AD; Amendment 

39–17628; AD 2013–20–51] 

RIN 2120–AA64 

Airworthiness Directives; 

AgustaWestland S.p.A. (Agusta) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

Model A109A, A109A II, A109C, 

A109E, A109K2, A109S, AW109SP, 

A119, and AW119 MKII helicopters. 

The emergency AD was sent previously 

to all known U.S. owners and operators 

of these helicopters. This AD requires, 

before further flight, inspecting certain 

Thomas coupling nuts on the tail rotor 

drive shaft line for a crack and replacing 

all the nuts if any nut is cracked. Also 

this AD requires replacing all affected 

Thomas coupling nuts within 10 hours 

time-in-service (TIS) or 30 days, 

whichever occurs first. This AD was 

prompted by two incidents of cracking 

on the nuts that connect the flexible 

disc coupling (Thomas coupling) with 

the splined adapter on the tail rotor 

drive shaft. We are issuing this AD to 

correct the unsafe condition on these 

helicopters. 

DATES: This AD is effective October 25, 

2013 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2013–20–51, 

issued on October 3, 2013, which 

contained the requirements of this 

amendment. 

We must receive comments on this 

AD by December 24, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the foreign 

authority’s AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. 

For service information identified in 

this AD, contact Agusta Westland, 

Customer Support & Services, Via Per 

Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http://

www.agustawestland.com/technicalbullettins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone: (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 3, 2013, we issued 

Emergency AD 2013–20–51, which 

requires, before further flight, inspecting 

certain Thomas coupling nuts on the tail 

rotor drive shaft line for a crack and 

replacing all the nuts if any nut is 

cracked. Also the emergency AD 

requires replacing all affected Thomas 

coupling nuts within 10 hours TIS or 30 

days, whichever occurs first. This 

emergency AD was sent previously to 

all known U.S. owners and operators of 

these helicopters. This action was 

prompted by two incidents of cracking 

on the nuts that connect the flexible 

disc coupling (Thomas coupling) with 

the splined adapter on the tail rotor 

drive shaft. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2013– 


emcdonald on DSK67QTVN1PROD with RULES